Fan track liner

文档序号：914229 发布日期：2021-02-26 浏览：19次中文

阅读说明：本技术 风扇轨道衬里 (Fan track liner ) 是由里卡多·佩林于 2019-07-03 设计创作，主要内容包括：一种制造用于燃气涡轮发动机的风扇容纳布置的风扇轨道衬里或风扇轨道衬里预成型件的方法,所述方法包括通过增材制造装置将纤维增强聚合物材料沉积到旋转心轴上以形成彼此一体的多孔撞击结构和支撑子层压件。(A method of manufacturing a fan rail liner or a fan rail liner preform for a fan containment arrangement of a gas turbine engine, the method comprising depositing a fibre reinforced polymer material onto a rotating mandrel by an additive manufacturing device to form a porous impingement structure and a support sub-laminate integral with one another.)

1. A method of manufacturing a fan rail liner or a fan rail liner preform for a fan containment arrangement of a gas turbine engine, the method comprising: depositing a fiber reinforced polymer material onto a rotating mandrel by an additive manufacturing device to form a porous impingement structure and a support sub-laminate integral with each other.

2. A method of manufacturing a fan rail liner or a fan rail liner preform for a fan containment arrangement of a gas turbine engine, the method comprising: depositing a fiber reinforced polymer material onto an inside surface of a fan containment case or fan containment case preform, such as an adhesive coated inside surface of the fan containment case or fan containment preform, by an additive manufacturing device to form a porous impingement structure and a support sub-laminate integral with one another; and optionally, curing the fan rail liner preform and/or the fan containment case preform, if present.

3. The method of claim 1 or claim 2, further comprising: providing or fabricating a digital model for the fan rail liner or the fan rail liner preform; and controlling the additive manufacturing apparatus using the digital model to deposit fiber reinforced polymer material to form the porous impingement structure and the support sub-laminate.

4. The method of claim 1, further comprising: laying up a fan containment case preform around a fan track liner or fan track liner preform formed on a rotating mandrel; and curing the fan containment case preform and, optionally, if present, the fan track liner preform.

5. The method of claim 1 or claim 2, wherein depositing the fiber reinforced polymer material comprises depositing a fiber reinforced polymer material to form the fan rail liner or a first portion of the fan rail liner preform, and the method further comprises:

forming a ballistic resistant barrier layer on a first portion of the fan rail liner or the fan rail liner preform by applying a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt; and

depositing a fiber reinforced polymer material on and around the ballistic resistant barrier layer by an additive manufacturing device to form a second portion of the fan rail liner or the fan rail liner preform, thereby encapsulating the ballistic resistant barrier layer between the first portion and the second portion of the fan rail liner or the fan rail liner preform; and

optionally, curing the fan track liner preform.

6. A fan track liner for a fan containment arrangement of a gas turbine engine, the fan track liner comprising a porous impingement structure and a support sub-laminate integrally formed with one another from a fiber reinforced polymer material, wherein the fan track liner further comprises a ballistic barrier comprising a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt.

7. The fan track liner of claim 6 wherein the porous impingement structure is a honeycomb structure.

8. The fan rail liner of claim 6 or claim 7 wherein the porous impingement structure and the strut laminate are integrally formed with one another by additive manufacturing.

9. The fan track liner of any of claims 6 to 8 wherein the fiber reinforced polymer material comprises reinforcing fibers made from one or more of the following materials: carbon, aramid polymer, ultra-high molecular weight polyethylene, PBO.

10. The fan track liner of any of claims 6 to 9 comprising two porous impingement structures separated from each other by a diaphragm layer formed from a support sub-laminate, and optionally wherein the two porous impingement structures have different cell densities.

11. The fan rail liner according to any one of claims 6 to 10, comprising two support panel sub-laminates, wherein one of the support panel sub-laminates forms an inner side of the fan rail liner and the other support panel sub-laminate forms an outer side of the fan rail liner, thereby forming a sandwich structure in which the porous impingement structure is located between the two support panel sub-laminates.

12. A fan containment arrangement for a gas turbine engine, the fan containment arrangement comprising a fan containment case and a fan track liner according to any one of claims 6 to 11.

13. A digital design model for a fan track liner according to any one of claims 6 to 11.

14. A computer program comprising instructions for causing an additive manufacturing apparatus to perform a method according to any one of claims 1 to 5 and/or to fabricate a fan track liner according to any one of claims 6 to 11.

15. A non-transitory computer readable medium storing a digital design model according to claim 13 and/or a computer program according to claim 14.

16. A data carrier signal carrying the digital design model according to claim 13 and/or the computer program according to claim 14.

17. A fan track liner for a fan containment arrangement of a gas turbine engine, the fan track liner comprising an embedded ballistic barrier comprising a woven layer of reinforcing fibers and a layer of reinforcing fiber felt, wherein optionally the woven layer of reinforcing fibers is disposed outside the layer of reinforcing fiber felt.

18. The fan track liner of claim 17 further comprising a porous impingement structure.

19. The fan track liner of claim 18 comprising two porous impingement structures separated from each other by a membrane layer comprising the ballistics barrier.

20. The fan track liner of any of claims 17 to 19 wherein the woven reinforcement fiber plies and the reinforcement fiber batt layers each comprise reinforcement fibers made from one or more of the following materials: carbon, aramid polymer, ultra-high molecular weight polyethylene, PBO.

21. A fan containment arrangement for a gas turbine engine, the fan containment arrangement comprising a fan containment case and a fan track liner according to any one of claims 17 to 20.

22. A method of manufacturing a fan track liner for a fan containment arrangement of a gas turbine engine, the method comprising:

depositing a fibre reinforced polymer material, for example by an additive manufacturing device, to form a first portion of a fan rail liner or a fan rail liner preform;

depositing a fiber-reinforced polymer material on and around the anti-ballistic barrier layer, for example by an additive manufacturing device, to form a second portion of the fan rail liner or fan rail liner preform, thereby encapsulating the anti-ballistic barrier layer between the first and second portions of the fan rail liner or fan rail liner preform; and the number of the first and second groups,

optionally, curing the fan track liner preform.

Technical Field

The present disclosure relates to fan track liners and methods of manufacturing fan track liners.

Background

The gas turbine engine includes a fan having fan blades located forward of the engine. The fan may be accommodated in the fan accommodating case. In the event of a failure during operation, one of the fan blades may break off of the fan and strike the fan containment case. This is commonly referred to as a Fan Blade Out (FBO) event. After a turbine engine fan loses blades, the load on the fan containment case due to fan strike is much higher than the load experienced under normal flight conditions. During engine shutdown (typically on the order of a few seconds), cracks can propagate rapidly in the fan containment case due to damage caused by the impact of the FBO, which can lead to containment failure.

A fan track liner is typically provided on the inside surface of the fan containment case. The fan track liner may comprise one or more layers of porous material, such as honeycomb aluminum or foamed aluminum, which may be sandwiched between and bonded to supporting fiber reinforced laminate layers. The fan rail liner is designed to absorb some of the energy that strikes the blades during an FBO event.

The manufacture of a fan containment arrangement that includes a fan track liner in combination with a fan containment case can be complex and time consuming. It has also been observed that composite fan track liners have a tendency to structurally deform when cured (e.g., when combined with a fan containment case). Indeed, shrinkage of the fan track liner upon final curing of the fan containment arrangement may also result in structural distortion of the surrounding fan containment case.

Disclosure of Invention

According to a first aspect, a fan rail liner for a fan containment arrangement of a gas turbine engine is provided, the fan rail liner comprising a porous impingement structure and a support sub-laminate integrally formed with one another from a fiber reinforced polymer material.

Since the porous impingement structure and the support sub-laminate are formed integrally with each other from a fiber reinforced polymer material, the thermal behavior of the porous impingement structure (i.e. the behavior of the porous impingement structure in response to heating and/or cooling) may be substantially the same as the thermal behavior of the support sub-laminate. For example, it may be the case that the porous impingement structure and support sub-laminate expand or contract relatively uniformly when heated or cooled. It may be that the coefficient of thermal expansion of the porous strike structure (i.e. the material from which the porous strike structure is formed) is similar (e.g. the same) to the coefficient of thermal expansion of the support sub-laminate (i.e. the material from which the support sub-laminate is formed). It may be that the coefficient of thermal expansion is substantially uniform throughout the porous strike structure and support sub-laminate. For example, it may be the case that the coefficient of thermal expansion of the porous strike structure is at most 10% greater (e.g., at most 5% greater, or at most 3% greater, or at most 1% greater) than the coefficient of thermal expansion of the support sub-laminate, and at most 10% less (e.g., at most 5% less, or at most 3% less, or at most 1% less) than the coefficient of thermal expansion of the support sub-laminate. As a result, structural distortion of the fan track liner upon heating or cooling (e.g., during a curing cycle) may be reduced (e.g., minimized).

The porous impingement structure may be a honeycomb structure. The honeycomb structure may include a plurality of cells formed between cell walls. The cells may be substantially hollow. A honeycomb structure may be described as a network of connected cell walls at least partially enclosing a plurality of cells (e.g., substantially hollow cells). The cell walls may be thin relative to the cell size. For example, the cell walls can have a thickness of no greater than 10% (e.g., no greater than 5%, or no greater than 1%) of a characteristic cell size (e.g., cell width). The cell walls may also be thin in thickness relative to the porous strike structure. The cells may be regularly arranged on the grid. The cells may be columnar. The cells may be columnar and arranged substantially parallel to each other, i.e., such that the longitudinal axis of each columnar cell is substantially parallel to the longitudinal axis of each other columnar cell.

The honeycomb structure may be a hexagonal honeycomb structure. The honeycomb structure may include columnar cells having a hexagonal cross section. The honeycomb may be an expanded honeycomb (i.e., "over-expanded" honeycomb), a reinforced hexagonal honeycomb (i.e., a predominantly hexagonal honeycomb reinforced by additional cell walls), or a rectangular honeycomb. The honeycomb structure may include a periodically repeating pattern of cell walls. The repeating pattern may be regular. The repeating pattern may be layered. The repeating pattern may form cells having two or more, or three or more, or four or more cell shapes that differ.

The porous impingement structure may have a density of no greater than about 200kg/m³E.g., not greater than about 180kg/m³Or not more than about 160kg/m³Or not greater than about 150kg/m³. The porous impingement structure may have a density of no less than about 10kg/m³For example, not less than about 25kg/m³Or not less than about 50kg/m³. The density of the cellular impact structure may be from about 10kg/m³To about 200kg/m³E.g. from about 25kg/m³To about 180kg/m³Or from about 50kg/m³To about 160kg/m³Or from about 50kg/m³To about 150kg/m³。

The relative density R of the cellular impact structure can be defined as

Where ρ is^*Is the density of the porous impingement structure, and ρ is the density of the solid material (i.e., the fiber reinforced polymer material) forming the porous impingement structure (i.e., the porous impingement structure walls). The porous strike structure can have a relative density R of not greater than about 0.5, for example, not greater than about 0.4, or not greater than about 0.3, or not greater than about 0.2.

It may be that the average cell diameter (i.e., cell size) of the porous, impact structure is not greater than about 20mm, such as not greater than about 15mm, or not greater than about 10mm, or not greater than about 7 mm. It may be that the average cell diameter of the cellular impact structure is not less than about 0.1mm, for example, not less than about 1mm, or not less than about 2mm, or not less than about 3 mm. It may be that the average cell diameter of the cellular impact structure is from about 0.1mm to about 20mm, for example, from about 1mm to about 15mm, or from about 1mm to about 10mm, or from about 3mm to about 10 mm.

For a cellular impact structure having a honeycomb structure with columnar cell walls, the maximum in-plane cell diameter can be defined as the maximum straight-line distance between opposing cell walls as measured on a cross-section through cells perpendicular to the cell walls. For a cellular impact structure having a honeycomb structure with columnar cell walls, the minimum in-plane cell diameter can be defined as the smallest straight-line distance between opposing cell walls as measured on a cross-section through cells perpendicular to the cell walls.

It may be that the maximum in-plane cell diameter of the porous impingement structure is no greater than about 20mm, for example, no greater than about 15mm, or no greater than about 10mm, or no greater than about 7 mm. It may be that the maximum in-plane cell diameter of the cellular impact structure is not less than about 0.1mm, for example, not less than about 1mm, or not less than about 2mm, or not less than about 3 mm. It may be that the maximum in-plane cell diameter of the porous impingement structure is from about 0.1mm to about 20mm, for example, from about 1mm to about 15mm, or from about 1mm to about 10mm, or from about 3mm to about 10 mm.

It may be that the cell diameter in the smallest plane of the porous impingement structure is no greater than about 20mm, for example, no greater than about 15mm, or no greater than about 10mm, or no greater than about 7 mm. It may be that the smallest in-plane cell diameter of the cellular impact structure is not less than about 0.1mm, for example, not less than about 1mm, or not less than about 2mm, or not less than about 3 mm. It may be that the smallest in-plane cell diameter of the porous impingement structure is from about 0.1mm to about 20mm, for example, from about 1mm to about 15mm, or from about 1mm to about 10mm, or from about 5mm to about 10 mm.

The porous impingement structure may comprise substantially hollow cells. It may be that a majority (e.g., all) of the cells in the porous strike structure are substantially hollow.

It may be the case that some, such as most (e.g., all) of the cells in the porous impingement structure are filled with gas. For example, it may be the case that some, such as most (e.g., all) of the cells in the porous impingement structure are filled with air. It may be that at least some (e.g., most or substantially all) of the cells of the porous impingement structure are gas-filled cells, e.g., air-filled cells.

The support sub-laminate may be solid. The support sub-laminate may be a solid layer of fibre reinforced polymer material. The support sub-laminate may be a unitary sheet of solid fibre reinforced polymer material.

The support sub-laminate may comprise a substantially two-dimensional (e.g. planar) arrangement of reinforcing fibres. It should be understood that although the shape of the fan track liner is generally curved (e.g., annular or cylindrical), a two-dimensional plane in which the reinforcing fibers are arranged may be defined locally (i.e., tangentially). For example, the reinforcing fibers may be arranged axially along the fan track liner, or circumferentially around the fan track liner, or in a direction intermediate the axial or circumferential orientations. However, the reinforcing fibers are generally not aligned in a radial direction or a direction having a substantial radial component.

The support sub-laminate may be substantially unidirectional, i.e. the reinforcing fibres in the support sub-laminate may be oriented predominantly in the same direction. Alternatively, the support sub-laminate may be multiaxial, i.e. the reinforcing fibres in the support sub-laminate may be arranged in two or more layers with different fibre orientations. For example, the support sub-laminate may comprise a first layer and a second layer, wherein in the first layer the reinforcing fibers are predominantly oriented in a first direction, and wherein in the second layer the reinforcing fibers are oriented in a second direction different from the first direction.

The fan track liner may include a ballistics barrier. The ballistics barrier may be configured to decelerate an impacting projectile (such as impacting a fan blade during an FBO event) and reduce the likelihood of the impacting projectile penetrating the surrounding fan containment case when in use.

The ballistic abatement barrier may comprise one or more layers of reinforcing fiber sheets.

The ballistic abatement barrier may comprise a woven reinforcing fiber sheet. It will be understood that a woven reinforcement fiber sheet is a fabric sheet woven from reinforcement fibers by interweaving warp and weft reinforcement fibers in a repeating pattern. The braided reinforcing fiber plies may have one or more of the following braids: plain weave, twill, section weave, basket weave, leno, mock leno. The woven reinforcing fiber plies may provide strength to the ballistics barrier.

The ballistic barrier can include a layer of reinforcing fiber mat. It should be understood that the reinforcement fiber mat is a textile formed from randomly oriented and/or delustered reinforcement fibers. The reinforcement fiber mat may be formed of continuous or discontinuous (e.g., long or chopped) reinforcement fibers. The reinforcing fiber mat layer may improve the ability of the ballistic barrier to absorb energy upon impact by a projectile. The reinforcing fiber mat layer may also form a soft blanket around the sharp edges of the impact projectile, effectively blunting those sharp edges.

The ballistic barrier can include a woven reinforcing fiber sheet layer and a reinforcing fiber felt layer. The mat of reinforcing fibres may be arranged inside the woven layer of reinforcing fibres. The woven reinforcement fiber sheet layer and the reinforcement fiber mat layer may be in direct contact with each other. Alternatively, the woven reinforcement fiber sheet layer and the reinforcement fiber mat layer may be spaced apart from each other. An air gap may be provided between the woven reinforcement fiber sheet layer and the reinforcement fiber batt layer. Upon impact of a projectile, such as a fan blade, the reinforcement fiber mat may absorb the impact energy and soften the sharp edges of the impacting projectile, thereby decelerating the projectile and reducing the likelihood of the projectile penetrating the woven reinforcement fiber plies.

The ballistic abatement barrier may comprise more than one layer of woven reinforcing fiber sheets. The ballistic abatement barrier may comprise more than one layer of reinforcing fiber mat. The fan track liner may include more than one ballistics barrier.

The ballistics barrier may be embedded within the fan track liner. The ballistic barrier or at least the reinforcing fiber mat layer may be completely encapsulated by the surrounding material. Encapsulation of the ballistic barrier, particularly the reinforcing fiber mat, can reduce the absorption of moisture by the reinforcing fiber mat.

The porous impingement structure and the support sub-laminate may be integrally formed with each other by additive manufacturing. It should be understood that the term "additive manufacturing" refers to computer-controlled deposition of materials for building up a three-dimensional part structure, and may be contrasted with "subtractive manufacturing" in which material is sequentially removed by machining to obtain a desired part structure. Additive manufacturing may sometimes be referred to as "3D printing.

Additive manufacturing includes processes known as "fused deposition modeling" (FDM) or "fused filament fabrication" (FFF) in which a part is manufactured by additionally applying materials in layers, typically by feeding plastic or wire through an extruder head, to deposit the molten material onto a substrate. Thus, the porous impingement structure and the support sub-laminate may be integrally formed with each other by fused deposition modeling or fuse fabrication.

The porous impingement structure and the support sub-laminate may be integrally formed with one another by additive manufacturing (e.g., FDM or FFF) such that the material forming the porous impingement structure is continuous with the material forming the support sub-laminate.

The porous impingement structure and the support sub-laminate may be integrally formed with one another by additive manufacturing (e.g., FDM or FFF) such that there is no discernable interface between the porous impingement structure and the support sub-laminate (e.g., when viewing a cross-section cut through the fan track liner).

The porous impingement structure and the support sub-laminate may be integrally formed with one another by additive manufacturing (e.g., FDM or FFF) such that reinforcing fibers extend between the porous impingement structure and the support sub-laminate.

It will be appreciated that fibre reinforced polymer materials typically comprise reinforcing fibres suspended in a polymer matrix material.

The polymer matrix material may be a thermoplastic polymer (i.e. a thermoplastic). Alternatively, the polymer matrix material may be a thermoset polymer (i.e., a thermoset).

The polymer matrix material may include (e.g., consist of) one or more of the following materials: epoxy glues (i.e. epoxy resins), polyesters, vinyl esters, polyamides (e.g. aliphatic or semi-aromatic polyamides, such as nylon), polylactide, polycarbonate, acrylonitrile butadiene styrene, Polyetheretherketone (PEEK), Polyetherimide (PEI).

The fiber reinforced polymer material may include carbon reinforcing fibers. The fibre reinforced polymer material may be a Carbon Fibre Reinforced Polymer (CFRP).

The fiber reinforced polymer material may include aromatic hydrocarbonsA nylon (i.e., an aromatic polyamide) reinforcing fiber. The fiber reinforced polymer material may include para-aramid reinforcing fibers. For example, the fiber-reinforced polymeric material may include a blend of poly-p-phenylene terephthalamideOr p-phenylene terephthalamideThe formed reinforcing fibers.

The fiber reinforced polymer material may include reinforcing fibers formed from a thermoset liquid crystal polyoxazole. For example, the fiber-reinforced polymer material may include a blend of poly-p-phenylene-2, 6-benzobisoxazole (PBO or PBO)) The formed reinforcing fibers.

The fibre-reinforced polymer material may comprise reinforcing fibres formed from polyethylene, for example Ultra High Molecular Weight Polyethylene (UHMWPE). The molecular weight of the UHMWPE may be from about 350 to about 750 million amu.

The fiber reinforced polymer material may include continuous reinforcing fibers. The fiber reinforced polymer material may include discontinuous (e.g., chopped) reinforcing fibers.

The porous impingement structure and the support sub-laminate may be integrally formed with each other (e.g., additively manufactured together) from the same fiber reinforced polymer material.

The porous impact structure and the support sub-laminate may be integrally formed with one another (e.g., additively manufactured) from the same fiber reinforced polymer material such that the coefficient of thermal expansion of the porous impact structure and the coefficient of thermal expansion of the support sub-laminate are substantially the same. For example, it may be the case that the coefficient of thermal expansion varies by no more than 10%, for example, no more than 5%, or no more than 3%, or no more than 1% across the porous impact structure and support sub-laminate. It may be that the coefficient of thermal expansion does not vary by more than 10%, for example, by more than 5%, or by more than 3%, or by more than 1%, across the fan track liner.

The woven reinforcement fiber plies may include reinforcement fibers (e.g., woven from reinforcement fibers) made from one or more of the following materials: carbon, aramid polymers (e.g., para-aramid polymers such as poly-p-phenylene terephthalamide or p-phenylene terephthalamide), ultra high molecular weight polyethylene, thermosetting liquid crystal polyoxazoles (e.g., poly-p-phenylene-2, 6-benzobisoxazole).

The reinforcement fiber mat may include reinforcement fibers made from one or more of the following materials: carbon, aramid polymers (e.g., para-aramid polymers such as poly-p-phenylene terephthalamide or p-phenylene terephthalamide), ultra high molecular weight polyethylene, thermosetting liquid crystal polyoxazoles (e.g., poly-p-phenylene-2, 6-benzobisoxazole).

The fan track liner may comprise two or more of said porous impingement structures. The individual porous impact structures may be separated from each other by corresponding membrane layers. The respective membrane layers may be formed from a support sub-laminate. One or more of the membrane layers (e.g., each membrane layer) may include a ballistic resistant barrier. One or more of the barrier layers (e.g., each barrier layer) may be formed from a ballistic resistant barrier.

It may be the case that some or each of the cellular impact structures have different cell densities. It may be the case that some or each of the cellular impact structures have different cell geometries.

For example, the fan track liner may include two porous impingement structures. The fan track liner may include two porous impingement structures separated from each other by a diaphragm layer. The membrane layer may be formed from a support sub-laminate. The membrane layer may include a ballistic barrier. The membrane layer may be formed from a ballistic barrier.

It may be the case that the two cellular impact structures have different cell densities. It may be that the two cellular impact structures include an outer cellular impact structure and an inner cellular impact structure, wherein the outer cellular impact structure has a cell density that is lower than the cell density of the inner cellular impact structure.

It may be the case that the two cellular impingement structures have different cell geometries. It may be that one or both of the cellular impingement structures are optimally angled cellular impingement structures. It may be that the outer cellular impingement structure is an optimally angled cellular impingement structure. It may be the case that the cell walls of the cellular impingement structure at the optimum angle are arranged to align with the projected path of the fan blade during an FBO event.

It may be the case that both porous impingement structures have a honeycomb structure. It may be the case that the outer cellular impingement structure has a honeycomb structure with an optimum angle.

The fan track liner may comprise a support panel sub-laminate. The support panel sub-laminate may form an inner side of the fan track liner. The support panel sub-laminate may form an outer side of the fan track liner. The support panel sub-laminate may be integrally formed (e.g., additively manufactured) with the porous strike structure of fiber reinforced polymer material and/or the support sub-laminate. The support panel sub-laminate may be a support sub-laminate integrally formed with a porous strike structure of fibre reinforced polymer material.

The fan track liner may include two support panel sub-laminates. One of the two support panel sub-laminates may form an inner side of the fan track liner. The other of the two support panel sub-laminates may form an outer side of the fan track liner. The two support panel sub-laminates may together form a sandwich structure in which the porous impingement structure is located between the two support panel sub-laminates. The two support panel sub-laminates may be integrally formed (e.g. additive manufactured) with the porous impact structure of fibre reinforced polymer material and/or the support sub-laminate. One of the two support panel sub-laminates may be a support sub-laminate integrally formed with a porous strike structure of a fibre reinforced polymer material. For example, the fan track liner may comprise a porous impingement structure, a support panel sub-laminate (which is a first support panel sub-laminate), and another support panel sub-laminate (which is a second support panel sub-laminate), the first and second support panel sub-laminates forming a sandwich structure, wherein the porous impingement structure is located between the first and second support panel sub-laminates, wherein the porous impingement structure, the first and second support panel sub-laminates are integrally formed with each other (e.g., additively manufactured) from a fiber reinforced polymer material.

The fan track liner may further comprise a wear resistant structure. The wear resistant structure may be located on the innermost side of the fan track liner. The wear resistant structure may be located on the innermost support panel sub-laminate. The wear resistant structure may be configured to be worn by the movement of the fan blades during jet engine operation to provide a close fit between the fan containment arrangement and the fan blades and to minimize air leakage around the tips of the fan blades. The wear-resistant structure has a porous structure, i.e. the wear-resistant structure can be a porous wear-resistant structure. The porous wear resistant structure may have a foam structure. The porous wear resistant structure may have a honeycomb structure. The porous wear resistant structure may be integrally formed (e.g. additively manufactured) from a fibre reinforced polymer material with the porous impact structure and/or the support sub-laminate and/or one of the plurality of support panel sub-laminates.

It may be the case that a large portion of the fan track liner is formed of (i.e. the same) fibre reinforced polymer material. It may be that at least 50%, such as at least 60%, or at least 70%, or at least 80%, or at least 90%, or at least 95% of the mass of the fan track liner consists of (i.e. is the same as) the fibre-reinforced polymer material. It may be that at least 50%, such as at least 60%, or at least 70%, or at least 80%, or at least 90%, or at least 95% of the material volume of the fan track liner consists of (i.e. is the same as) the fiber reinforced polymer material.

It may be the case that the entire fan track liner is formed from (i.e. the same) fibre reinforced polymer material. Alternatively, it may be the case that the entire fan track liner is formed of (i.e. the same) fibre reinforced polymer material, except for the ballistics barrier.

The fan containment arrangement may include a fan containment case and a fan track liner. The fan containment case may be configured to provide structural support for the fan track liner.

The fan rail liner may be used as a fan impingement liner, i.e., the fan rail liner may be a fan impingement liner. The fan containment arrangement may further comprise a sound dampening liner. The sound suppression liner may be disposed forward or rearward of the fan track liner (i.e., the fan impingement liner). The fan containment arrangement may include two sound suppression liners, one sound suppression liner disposed forward of the fan track liner (i.e., the fan impingement liner) and the other sound suppression liner disposed rearward of the fan track liner (i.e., the fan impingement liner).

The or each sound dampening liner may be formed from a fibre reinforced polymer material, for example by additive manufacturing. The or each sound damping liner may be integrally formed with the fan track liner (i.e. the fan impingement liner) from a fibre reinforced polymer material, for example by additive manufacturing. The or each sound suppression liner may comprise a porous resonant structure and one or more support sub-laminates integrally formed with one another from fibre reinforced polymer material, for example by additive manufacturing. The porous resonance structure may have a honeycomb structure.

According to a second aspect, there is provided a fan containment arrangement for a gas turbine engine, the fan containment arrangement comprising a fan containment case and a fan track liner according to the first aspect of the invention.

The fan containment case may be configured to provide structural support for the fan track liner.

A fan track liner may be disposed on an inside surface of the fan containment case. The fan rail liner may be mounted on an inside surface of the fan containment case. The fan track liner may be adhered or bonded to the inside surface of the fan containment case. The fan track liner may be integrally formed with the fan containment case, such as on the inside integrally formed with the fan containment case.

The fan track liner may be used as a fan impingement liner in a fan containment arrangement, i.e. the fan track liner may be a fan impingement liner. The fan containment arrangement may further comprise a sound dampening liner. The sound suppression liner may be disposed forward or rearward of the fan track liner (i.e., the fan impingement liner). The fan containment arrangement may include two sound suppression liners, one sound suppression liner disposed forward of the fan track liner (i.e., the fan impingement liner) and the other sound suppression liner disposed rearward of the fan track liner (i.e., the fan impingement liner).

The fan receiving case may include a front portion, a middle portion, and a rear portion along an axial extent thereof. The axial extent of the fan containment case may correspond to an axial position of the fan when the fan containment case is installed in the gas turbine engine. The front and rear portions may be thinner than the middle portion. The thickness of each of the front and rear portions may decrease with distance away from the intermediate portion. A fan track liner may be disposed on an inside surface of the fan containment case in the intermediate portion. The fan track liner may be selectively located on an inside surface of the fan containment case at a portion of the fan containment case configured to surround the fan. During an FBO event, the fan rail liner may be selectively positioned in the estimated path of the fan blade. The fan rail liner may be selectively located on the inside surface of the fan containment case at the impact zone (i.e., at least one impact zone most likely to be impacted by the fan blades during an FBO event).

According to a third aspect, there is provided a method of manufacturing a fan rail liner or a fan rail liner preform for a fan containment arrangement of a gas turbine engine, the method comprising: depositing fiber reinforced polymer material by an additive manufacturing device to form a porous impingement structure and a support sub-laminate integral with each other. The method may be a method of manufacturing a fan rail liner according to the first aspect and/or a method of manufacturing a fan rail liner preform for a fan rail liner according to the first aspect.

The method may comprise depositing fibre reinforced polymer material by an additive manufacturing device to form more than one porous impingement structure, for example two porous impingement structures. The method may comprise depositing fibre reinforced polymer material by an additive manufacturing apparatus to form more than one support sub-laminate. The method may comprise depositing fibre reinforced polymer material by an additive manufacturing apparatus to form one or more support panel sub-laminates, for example two support panel sub-laminates. The method may comprise depositing fibre reinforced polymer material by the additive manufacturing apparatus to form one or more membrane layers between the porous impact structures. The method may comprise depositing fibre reinforced polymer material by an additive manufacturing device to form a wear resistant structure, for example a porous wear resistant structure.

The use of an additive manufacturing device significantly reduces the manufacturing time required to make a fan track liner, particularly as compared to the most common methods of manufacturing fan track liners, which involve forming individual component layers of a fan track liner separately and then assembling and bonding the component layers together to form a fan track liner.

The additive manufacturing device comprises a Fused Deposition Modeling (FDM) or a fuse manufacturing (FFF) device. The FDM or FFF apparatus may comprise an extruder head. The extruder head may be heated. The FDM or FFF apparatus may include means for feeding one or more filaments of material into and through the extruder head, such as a motor configured to pull one or more filaments of material into and through the extruder head. The heat and pressure applied to the one or more strands of material passing through the extruder head may cause at least a portion of the material to transition to a liquid state, thereby allowing for controlled deposition of the molten material onto the substrate.

For depositing the fiber reinforced polymer material, it may be the case that the additive manufacturing device (e.g., FDM or FFF device) receives the fiber reinforced polymer material as an input. The fiber-reinforced polymer material can be prepared, for example, by the following method: the reinforcing fibers and polymer (e.g., in the form of polymer pellets) are mixed in a mixer and the resulting mixture is extruded to form fiber reinforced polymer material filaments suitable for use in, for example, FDM or FFF devices. In such embodiments, the filaments of fiber reinforced polymer material received by the additive manufacturing device and/or the fiber reinforced polymer material deposited by the additive manufacturing device may include discontinuous (e.g., chopped) reinforcement fibers.

Alternatively, it may be the case that the additive manufacturing device (e.g., FDM or FFF device) receives the reinforcement fibers and polymer as separate inputs. For example, an additive manufacturing device may receive polymer filaments and reinforcing fiber filaments (e.g., continuous reinforcing fiber filaments). It may be the case that heating the polymer filaments and the reinforcement fibre filaments together within the extruder head of the additive manufacturing device results in impregnation of the reinforcement fibre filaments with the polymer. In such embodiments, the fiber reinforced polymer material deposited by the additive manufacturing device may comprise discontinuous or continuous reinforcing fibers. A similar method may be used to deposit a fiber reinforced polymer material comprising reinforcing fiber yarns. Examples of methods that allow for additive manufacturing using continuous fiber reinforced polymer materials can be found in the following documents: "Three-dimensional printing of continuous fiber composites by in-nozzle impregnation", R.Matsuzaki et al, Scientific Reports 6[ Scientific Reports 6], article number: 23058(2016), the entire contents of which are hereby incorporated by reference. Such a method may also provide control over the orientation of the deposited reinforcing fibers.

In another alternative, it may be the case that the additive manufacturing device (e.g., FDM or FFF device) receives as a single input a continuous reinforcing fiber filament (e.g., polymer coated continuous reinforcing fiber filament) comprising embedded polymer.

The deposited fiber-reinforced polymer material may comprise a thermoplastic polymer (i.e. thermoplastic) matrix material. Alternatively, the deposited fiber reinforced polymer material may comprise a thermoset polymer (i.e. thermoset) matrix material. The additive manufacturing device may receive a thermoplastic polymer or a thermoset polymer as an input.

The matrix material may comprise (e.g. consist of) one or more of the following materials: epoxy glues (i.e. epoxy resins), polyesters, vinyl esters, polyamides (e.g. aliphatic or semi-aromatic polyamides, such as nylon), polylactide, polycarbonate, acrylonitrile butadiene styrene, Polyetheretherketone (PEEK), Polyetherimide (PEI). The additive manufacturing device may receive as input one or more of the following materials, for example a filament comprising one or more of the following materials: epoxy glues (i.e. epoxy resins), polyesters, vinyl esters, polyamides (e.g. aliphatic or semi-aromatic polyamides, such as nylon), polylactide, polycarbonate, acrylonitrile butadiene styrene, Polyetheretherketone (PEEK), Polyetherimide (PEI).

The fiber reinforced polymer material may include carbon reinforcing fibers. The fibre reinforced polymer material may be a Carbon Fibre Reinforced Polymer (CFRP).

The fiber reinforced polymer material may include aramid (i.e., aromatic polyamide) reinforcing fibers. The fiber reinforced polymer material may include para-aramid reinforcing fibers. For example, the fiber-reinforced polymeric material may include a blend of poly-p-phenylene terephthalamideOr p-phenylene terephthalamideThe formed reinforcing fibers.

Thus, it may be the case that the fibre reinforced polymer material comprises reinforcing fibres made of one or more of the following: carbon, aramid polymers (e.g., para-aramid polymers such as poly-p-phenylene terephthalamide or p-phenylene terephthalamide), ultra high molecular weight polyethylene, thermosetting liquid crystal polyoxazoles (e.g., poly-p-phenylene-2, 6-benzobisoxazole). The additive manufacturing device may receive as input one or more reinforcing fibers (e.g. filaments of reinforcing fibers comprising one or more of the following materials) of: carbon, aramid polymers (e.g., para-aramid polymers such as poly-p-phenylene terephthalamide or p-phenylene terephthalamide), ultra high molecular weight polyethylene, thermosetting liquid crystal polyoxazoles (e.g., poly-p-phenylene-2, 6-benzobisoxazole).

The fiber reinforced polymer material may include continuous reinforcing fibers. The fiber reinforced polymer material may include discontinuous (e.g., chopped) reinforcing fibers. The additive manufacturing device may receive as input continuous reinforcing fibers. The additive manufacturing device may receive as input discontinuous (e.g., chopped) reinforcement fibers. The additive manufacturing device may receive as an input a reinforcing fiber yarn.

The method may comprise depositing fibre reinforced polymer material to form the porous impingement structure and the support sub-laminate in the same continuous process.

The method may comprise depositing the same fibre reinforced polymer material to form the porous impact structure and the support sub-laminate (and/or any of more than one porous impact structure, more than one support sub-laminate, one or more support panel sub-laminates, one or more membrane layers, or a wear resistant structure). Depositing the same fiber reinforced polymer material to form the structure may simplify and speed up the manufacturing process. Depositing the same fiber reinforced polymer material to form the structure may also result in a coefficient of thermal expansion that is effectively uniform across most (e.g., all) of the layers of the fan rail liner. Accordingly, the fan track liner may uniformly expand or contract in response to changes in temperature, resulting in a reduction (e.g., minimization) of structural distortion of the fan track liner during any curing or bonding processes. These distortions are generally more predictable, while any structural distortions are still present, and generally simplify modeling of the thermal response of the fan track liner.

The method may include providing or generating a digital model for a fan rail liner or a fan rail liner preform. The digital model may be provided in the form of a Computer Aided Design (CAD) file, such as an Additive Manufacturing File (AMF) or a Stereolithography (STL) file.

The method may comprise controlling the additive manufacturing apparatus using the digital model. The method may include depositing fiber reinforced polymer material to form the porous impingement structure and the support sub-laminate using a digital model controlled additive manufacturing device. For example, the method may include a controller controlling the additive manufacturing device using the digital model to deposit the fiber reinforced polymer material to form the porous strike structure and the support sub-laminate.

The controller may include a processor (in electronic communication with a memory storing computer executable program code) configured (e.g., programmed) to control the additive manufacturing device using the digital model to deposit the fiber reinforced polymer material to form the porous strike structure and the support sub-laminate.

The fan track liner formed by the method may be a fan impingement liner. The method may include depositing, by an additive manufacturing device, a fiber reinforced polymer material to form a porous resonant structure and one or more support sub-laminates, the porous resonant structure and the one or more support sub-laminates being integrally formed with one another to form an acoustic dampening lining. The porous resonance structure may have a honeycomb structure. The method may include depositing, by an additive manufacturing device, a fiber reinforced polymer material to form a sound suppression liner integrally formed with a fan track liner (i.e., a fan impingement liner). The method may comprise depositing fibre reinforced polymer material by an additive manufacturing apparatus to form more than one said sound suppression liner, the sound suppression liner being integrally formed with the fan track liner (i.e. the fan impingement liner).

The method may comprise depositing a fibre reinforced polymer material onto the tool. The method may include depositing a fiber reinforced polymer material onto a mandrel. The spindle may be rotatable. The method may include depositing a fiber reinforced polymer material onto a rotating mandrel.

The additive manufacturing apparatus may comprise one or more extruder heads movably mounted on a frame. The frame may be positioned above the mandrel. The method can comprise the following steps: positioning a frame over a mandrel; rotating the mandrel; and depositing fiber reinforced polymer material (i.e., through one or more extruder heads) on a rotating mandrel to form the porous impingement structure and support sub-laminate. In embodiments where the fiber reinforced polymer material comprises a thermoset polymer, the method may further comprise curing the fiber reinforced polymer material, for example, by applying heat and/or pressure (e.g., in an autoclave).

Alternatively, the method may comprise depositing a fibre reinforced polymer material onto an inside surface of the fan containment case or fan containment case preform. The method may include depositing a fiber reinforced polymer material on the adhesive coated inside surface of the fan containment case or fan containment case preform.

The additive manufacturing apparatus may comprise one or more extruder heads mounted on a moveable arm. The method can comprise the following steps: positioning an arm inside a fan containment case or fan containment case preform; and depositing a fiber reinforced polymer material (i.e., through one or more extruder heads) onto an inside surface of the fan containment case or fan containment case preform. The method may include moving (e.g., rotating) the fan containment case or fan containment case preform about the arm during deposition. Alternatively, the method may comprise moving the arm around the inside of the fan containment case or fan containment case preform during deposition.

According to a fourth aspect, there is provided a method of manufacturing a fan containment arrangement for a gas turbine engine, the method comprising: forming a fan rail liner or a fan rail liner preform on a rotating mandrel by a method according to the third aspect; laying up a fan containment case preform around a fan track liner or fan track liner preform formed on a rotating mandrel; and curing the fan containment case preform, and optionally, the fan track liner preform (if present).

For example, the method may include: forming a fan track liner on a rotating mandrel by a method according to the third aspect; laying up a fan containment case preform around a fan track liner formed on a rotating mandrel; and curing the fan containment case preform. Alternatively, the method may comprise: forming a fan track liner preform on a rotating mandrel by a method according to the third aspect; laying up a fan containment case preform around a fan track liner preform formed on a rotating mandrel; and curing (e.g., simultaneously) the fan containment case preform and the fan track liner preform.

By forming the fan containment case around the fan track liner formed on the rotating mandrel, the overall manufacturing time required to manufacture the fan containment arrangement may be reduced, particularly as compared to the most common methods of forming fan containment arrangements involving assembling and bonding together multiple different layers of fan track liners, laying up and curing multiple different layers of fan containment cases, and bonding the fan track liner to the fan containment case.

According to a fifth aspect, there is provided a method of manufacturing a fan containment arrangement for a gas turbine engine, the method comprising: providing a fan containment case or a fan containment case preform; and forming a fan track liner or a fan track liner preform on an inside surface (e.g., an adhesive coated inside surface) of the fan containment case or fan containment case preform by the method according to the third aspect; and optionally curing the fan track liner preform and/or the fan containment case preform (if present).

For example, the method may include: providing a fan housing case; and forming a fan track liner on an inside surface (e.g., an adhesive coated inside surface) of the fan containment case by the method according to the third aspect. Alternatively, the method may comprise: providing a fan housing case; forming a fan track liner preform on an inside surface (e.g., an adhesive coated inside surface) of a fan containment case by a method according to the third aspect; and curing the fan rail liner preform. In another alternative, the method may comprise: providing a fan containment case preform; forming a fan track liner preform on an inside surface (e.g., an adhesive coated inside surface) of a fan containment case preform by a method according to the third aspect; and curing the fan rail liner preform and the fan containment case preform.

By forming the fan track liner directly on the inside surface of the fan containment case or fan containment case preform, the overall manufacturing time required to manufacture the fan containment arrangement may be reduced, particularly as compared to the most common methods of forming fan containment arrangements involving assembling and bonding together multiple different layers of the fan track liner, laying up and curing the multiple different layers of the fan containment case, and bonding the fan track liner to the fan containment case.

According to a sixth aspect, there is provided a digital design model for a fan track liner according to the first aspect. The digital model may be provided in the form of a Computer Aided Design (CAD) file, such as an Additive Manufacturing File (AMF) or a Stereolithography (STL) file.

According to a seventh aspect, there is provided a non-transitory computer readable medium storing the digital design model according to the sixth aspect.

According to an eighth aspect, there is provided a data carrier signal carrying the digital design model according to the sixth aspect.

According to a ninth aspect, there is provided a computer program comprising instructions for causing an additive manufacturing apparatus to perform a method according to the third aspect and/or to fabricate a fan track liner according to the first aspect. For example, it may be that the additive manufacturing apparatus comprises or is in electronic communication with a computer (e.g. a processor in a controller), and the computer program comprises instructions which, when the program is executed by the computer (e.g. by the processor), cause the additive manufacturing apparatus to perform the method according to the third aspect and/or to fabricate the fan track liner according to the first aspect.

According to a tenth aspect, there is provided a non-transitory computer readable medium storing a computer program according to the ninth aspect.

According to an eleventh aspect, there is provided a data carrier signal carrying the computer program according to the ninth aspect.

According to a twelfth aspect, there is provided a fan rail liner for a fan containment arrangement of a gas turbine engine, the fan rail liner comprising an embedded ballistics barrier comprising a woven reinforcement fiber sheet layer and a reinforcement fiber felt layer.

The ballistics barrier may be configured to decelerate an impacting projectile (such as impacting a fan blade during an FBO event) and reduce the likelihood of the impacting projectile penetrating the surrounding fan containment case when in use.

It will be understood that a woven reinforcement fiber sheet is a fabric sheet woven from reinforcement fibers by interweaving warp and weft reinforcement fibers in a repeating pattern. The braided reinforcing fiber plies may have one or more of the following braids: plain weave, twill, section weave, basket weave, leno, mock leno. The woven reinforcing fiber plies may provide strength to the ballistics barrier.

It should also be understood that the reinforcement fiber mat is a textile formed from randomly oriented and/or delustered reinforcement fibers. The reinforcement fiber mat may be formed of continuous or discontinuous (e.g., long or chopped) reinforcement fibers. The reinforcing fiber mat layer may improve the ability of the ballistic barrier to absorb energy upon impact by a projectile. The reinforcing fiber mat layer may also form a soft blanket around the sharp edges of the impact projectile, effectively blunting those sharp edges.

The mat of reinforcing fibres may be arranged inside the woven layer of reinforcing fibres. The woven reinforcement fiber sheet layer and the reinforcement fiber mat layer may be in direct contact with each other. Alternatively, the woven reinforcement fiber sheet layer and the reinforcement fiber mat layer may be spaced apart from each other. An air gap may be provided between the woven reinforcement fiber sheet layer and the reinforcement fiber batt layer. Upon impact of a projectile, such as a fan blade, the reinforcement fiber mat may absorb the impact energy and soften the sharp edges of the impacting projectile, thereby decelerating the projectile and reducing the likelihood of the projectile penetrating the woven reinforcement fiber plies.

The fan rail liner may include a support sub-laminate. The fan rail liner may include more than one support sub-laminate.

The fan track liner may include a porous impingement structure. The fan track liner may include two or more of the cellular impingement structures. The individual porous impact structures may be separated from each other by corresponding membrane layers. The respective membrane layers may be formed from a support sub-laminate. One of the membrane layers may include a ballistic barrier. One of the membrane layers may be formed by a ballistic barrier.

It may be the case that both porous impingement structures have a honeycomb structure. It may be the case that one or both of the cellular impact structures have a honeycomb structure. It may be the case that the outer cellular impingement structure has a honeycomb structure with an optimum angle.

It may be that the woven reinforcement fibre sheet and the reinforcement fibre mat each comprise reinforcement fibres made of one or more of the following materials: carbon, aramid polymers (e.g., para-aramid polymers such as poly-p-phenylene terephthalamide or p-phenylene terephthalamide), ultra high molecular weight polyethylene, thermosetting liquid crystal polyoxazoles (e.g., poly-p-phenylene-2, 6-benzobisoxazole).

The ballistic barrier or at least the reinforcing fiber mat layer may be completely encapsulated by the surrounding material. Encapsulation of the ballistic barrier, particularly the reinforcing fiber mat, can reduce the absorption of moisture by the reinforcing fiber mat.

According to a thirteenth aspect, there is provided a fan containment arrangement for a gas turbine engine, the fan containment arrangement comprising a fan containment case and a fan track liner according to the twelfth aspect. The fan containment case may be configured to provide structural support for the fan track liner.

According to a fourteenth aspect, there is provided a method of manufacturing a fan track liner for a fan containment arrangement of a gas turbine engine, the method comprising: depositing a fiber reinforced polymer material, such as by an additive manufacturing device, to form a first portion of a fan rail liner or a fan rail liner preform; forming a ballistic resistant barrier layer on a first portion of a fan rail liner or a fan rail liner preform by applying a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt; and depositing a fiber-reinforced polymer material on and around the ballistic resistant barrier layer, for example by an additive manufacturing device, to form a second portion of the fan rail liner or fan rail liner preform, thereby encapsulating the ballistic resistant barrier layer between the first portion and the second portion of the fan rail liner or fan rail liner preform. The method may further comprise curing the fan rail liner preform.

For example, the method may include: depositing a fiber reinforced polymer material, such as by an additive manufacturing device, to form a first portion of a fan track liner; forming a ballistic barrier layer on a first portion of a fan track liner by applying a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt; and depositing a fiber-reinforced polymer material on and around the ballistic resistant barrier layer, such as by an additive manufacturing device, to form a second portion of the fan track liner, thereby encapsulating the ballistic resistant barrier layer between the first portion and the second portion of the fan track liner. Alternatively, the method may comprise: depositing a fiber reinforced polymer material, such as by an additive manufacturing device, to form a first portion of a fan track liner preform; forming a ballistic resistant barrier layer on a first portion of a fan track liner preform by applying a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt; depositing a fiber-reinforced polymer material on and around the ballistic abatement barrier layer, for example by an additive manufacturing apparatus, to form a second portion of the fan rail liner preform, thereby encapsulating the ballistic abatement barrier layer between the first portion and the second portion of the fan rail liner preform; and curing the fan rail liner preform.

Depositing the fiber reinforced polymer material to form the first portion or the second portion of the fan rail liner or the fan rail liner preform may comprise depositing the fiber reinforced polymer material, for example by an additive manufacturing device, to form one or more of: porous impact structure, support sub-laminate, support panel sub-laminate, membrane layer, wear resistant structure.

The method may comprise using an additive manufacturing apparatus or method or a fibre reinforced polymer material (including component reinforcing fibres and polymer matrix material) as discussed herein in relation to any other aspect.

The woven reinforcement fiber plies and reinforcement fiber mats are not typically additive manufactured.

Applying the woven reinforcement fiber plies may include laying up the woven reinforcement fiber plies, for example, by hand or by machine. For example, applying the braided reinforcing fiber sheet layer may include wrapping the braided reinforcing fiber sheet layer around a first portion of the fan rail liner or fan rail liner preform. Alternatively, applying the woven reinforcing fiber plies may include applying a strip of woven reinforcing fibers, for example, using an Automated Tape Laying (ATL) process.

Applying the mat of reinforcing fibers may include laying up the mat of reinforcing fibers, for example, by hand or by machine. For example, applying the layer of reinforcement fiber mat may include wrapping a piece of reinforcement fiber mat around the first portion of the fan rail liner or fan rail liner preform.

The method may include providing or making a digital model for a fan rail liner or a fan rail liner preform. The digital model may be provided in the form of a Computer Aided Design (CAD) file, such as an Additive Manufacturing File (AMF) or a Stereolithography (STL) file. The method may include controlling an additive manufacturing device using a digital model to deposit fiber reinforced polymer material to form a first portion and a second portion of a fan rail liner or a fan rail liner preform.

The method may include forming a fan track liner around the tool. The method may include forming a fan track liner around the mandrel. The spindle may be rotatable. The method may include forming a fan rail liner or a fan rail liner preform around a rotating mandrel. Alternatively, the method may comprise forming a fan track liner or a fan track liner preform on an inside surface, e.g. an adhesive coated inside surface, of the fan containment case or fan containment case preform.

As noted elsewhere herein, the present disclosure may relate to a gas turbine engine. Such a gas turbine engine may include an engine core including a turbine, a combustor, a compressor, and a spindle connecting the turbine to the compressor. Such gas turbine engines may include a fan (with fan blades) located upstream of the engine core.

The arrangement of the present disclosure may be particularly, but not exclusively, advantageous for fans driven via a gearbox. Accordingly, the gas turbine engine may include a gearbox that receives an input from the spindle and outputs a drive to the fan to drive the fan at a lower rotational speed than the spindle. The input to the gearbox may come directly from the spindle or indirectly from the spindle, for example via a spur gear shaft and/or gears. The spindle may rigidly connect the turbine and compressor such that the turbine and compressor rotate at the same speed (with the fan rotating at a lower speed).

The gas turbine engine as described and/or claimed herein may have any suitable general architecture. For example, the gas turbine engine may have any desired number of shafts connecting the turbine with the compressor, such as one shaft, two shafts, or three shafts. By way of example only, the turbine connected to the spindle may be a first turbine, the compressor connected to the spindle may be a first compressor, and the spindle may be a first spindle. The engine core may also include a second turbine, a second compressor, and a second spindle connecting the second turbine with the second compressor. The second turbine, the second compressor and the second spindle may be arranged to rotate at a higher rotational speed than the first spindle. In such an arrangement, the second compressor may be positioned axially downstream of the first compressor. The second compressor may be arranged to receive the flow from the first compressor (e.g. directly, e.g. via a substantially annular duct).

The gearbox may be arranged to be driven by a spindle (e.g. the first spindle in the above example) which is configured (e.g. in use) to rotate at the lowest rotational speed. For example, the gearbox may be arranged to be driven only by the spindles (e.g. only the first spindle, not the second spindle in the above example) that are configured to rotate (e.g. in use) at the lowest rotational speed. Alternatively, the gearbox may be arranged to be driven by any one or more shafts, such as the first shaft and/or the second shaft in the above examples.

In any of the gas turbine engines as described and/or claimed herein, the combustor may be disposed axially downstream of the fan and compressor(s). For example, where a second compressor is provided, the combustor may be located directly downstream of (e.g., at the outlet of) the second compressor. By way of another example, where a second turbine is provided, the flow at the combustor outlet may be provided to the inlet of the second turbine. The combustor may be disposed upstream of the turbine(s).

The or each compressor (e.g. the first and second compressors as described above) may comprise any number of stages (e.g. a plurality of stages). Each stage may include a row of rotor blades and a row of stator blades, which may be variable stator blades (as the angle of incidence of the stator blades may be variable). The row of rotor blades and the row of rotor blades may be axially offset from each other.

The fan blades and/or airfoil portions of fan blades described and/or claimed herein may be fabricated from any suitable material or combination of materials. For example, at least a portion of the fan blade and/or airfoil may be at least partially fabricated from a composite material, such as a metal matrix composite material and/or an organic matrix composite material, such as carbon fiber. By way of another example, at least a portion of the fan blade and/or airfoil may be at least partially fabricated from a metal such as a titanium-based metal or an aluminum-based material (such as an aluminum lithium alloy) or a steel-based material. The fan blade may include at least two regions fabricated using different materials. For example, a fan blade may have a protective leading edge that may be manufactured using a material that is more resistant to impacts (e.g., from birds, ice, or other materials) than the rest of the blade. Such a leading edge may be manufactured, for example, using titanium or a titanium-based alloy. Thus, by way of example only, the fan blade may have a carbon fiber or aluminum-based body (e.g., an aluminum lithium alloy) with a titanium leading edge.

A fan as described and/or claimed herein may include a central portion from which fan blades may extend, for example, in a radial direction. The fan blades may be attached to the central portion in any desired manner. For example, each fan blade may include a clip that may engage with a corresponding slot in the hub (or disk). By way of example only, such clips may be of dovetail form that may be inserted into and/or engage corresponding slots in the hub/disk to secure the fan blade to the hub/disk.

The fan of a gas turbine as described and/or claimed herein may have any desired number of fan blades, such as 16, 18, 20, or 22 fan blades.

Those skilled in the art will appreciate that features described in relation to any of the above aspects may be applied to any other aspect mutatis mutandis, unless mutually exclusive. Furthermore, any feature described herein may be applied to any aspect and/or in combination with any other feature described herein, unless mutually exclusive. In particular: any features described in relation to the first aspect may be applied, mutatis mutandis, to the twelfth aspect, unless mutually exclusive; any features described in relation to the second aspect may be applied, mutatis mutandis, to the thirteenth aspect, unless mutually exclusive; and any feature described in relation to the third aspect may be applied, mutatis mutandis, to the fourteenth aspect, unless mutually exclusive.

Drawings

Embodiments will now be described, by way of example only, with reference to the accompanying drawings, in which:

FIG. 1 is a cross-sectional side view of a gas turbine engine;

FIG. 2 is a cross-sectional side view of a fan containment arrangement including a fan containment case, a fan track liner, and two acoustic liners;

FIG. 3 is a schematic cross-sectional view through a fan track liner and a portion of a fan containment case;

FIG. 4 includes two cross-sectional side views (a) and (b) of a fan track liner deposited on a mandrel by an additive manufacturing apparatus in two mutually orthogonal directions; and

FIG. 5 is a cross-sectional side view through an additive manufacturing device depositing a fan rail liner inside a fan containment case.

Detailed Description

Fig. 1 shows a gas turbine engine 10 having a main axis of rotation 9. The engine 10 comprises an air intake 12 and a propulsive fan 23 which generates two air flows: core airflow a and bypass airflow B. The gas turbine engine 10 includes a core 11 that receives a core airflow A. The engine core 11 includes, in axial flow series, a low pressure compressor 14, a high pressure compressor 15, a combustion apparatus 16, a high pressure turbine 17, a low pressure turbine 19, and a core exhaust nozzle 20. Nacelle 21 surrounds gas turbine engine 10 and defines bypass duct 22 and bypass exhaust nozzle 18. The bypass airflow B flows through the bypass duct 22. The fan 23 is attached to the low pressure turbine 19 via a shaft 26 and an epicyclic gearbox 30 and is driven by the low pressure turbine 19. The fan containment arrangement 31 extends around the fan 23 inside the nacelle 21.

In use, the core airflow A is accelerated and compressed by the low pressure compressor 14 and directed into the high pressure compressor 15 for further compression. The compressed air discharged from the high-pressure compressor 15 is led into a combustion device 16, where the compressed air is mixed with fuel and the mixture is combusted. The resulting hot combustion products are then expanded through and thereby drive the high pressure turbine 17 and the low pressure turbine 19 to provide some propulsive thrust before being discharged through the nozzle 20. The high pressure turbine 17 drives the high pressure compressor 15 by means of a suitable interconnecting shaft 27. The fan 23 typically provides the majority of the propulsive thrust. The epicyclic gearbox 30 is a reduction gearbox.

Other gas turbine engines to which the present disclosure may be applied may have alternative configurations. For example, such an engine may have an alternative number of compressors and/or turbines and/or an alternative number of interconnecting shafts. By way of another example, the gas turbine engine shown in FIG. 1 has split nozzles 20, 22, which means that the flow through the bypass duct 22 has its own nozzle that is separate from and radially outside of the core engine nozzle 20. However, this is not limiting, and any aspect of the disclosure may also be applied to the following engines: in this engine, the flow through the bypass duct 22 and the flow through the core 11 are mixed or combined before (or upstream of) a single nozzle (which may be referred to as a mixed flow nozzle). One or both nozzles (whether mixed or split) may have a fixed or variable area. Although the described examples relate to a turbofan engine, the present disclosure may be applied, for example, to any type of gas turbine engine such as an open rotor (where the fan stages are not surrounded by a nacelle) or a turboprop engine. In some arrangements, the gas turbine engine 10 may not include the gearbox 30.

The geometry of gas turbine engine 10 and its components are defined by a conventional shafting including an axial direction (aligned with axis of rotation 9), a radial direction (direction from bottom to top in fig. 1), and a circumferential direction (perpendicular to the page in the view of fig. 1). The axial direction, the radial direction and the circumferential direction are perpendicular to each other.

The structure of the fan containment arrangement is illustrated in more detail in fig. 2, which shows a cross-sectional view of a portion of the fan containment arrangement 31.

The fan containment arrangement 31 includes a fan containment case 32 having an intermediate portion (barrel) 33 extending between a forward portion (i.e., front flange) 34 and a rearward portion (i.e., rear flange) 35. The fan containment case 32 is formed mainly of a fiber reinforced composite material and is located around the fan 23.

A fan impingement liner 36 is adhered to the inside surface of the intermediate portion 33 of the fan containment case 32. The fan impingement liner 36 has a predominantly porous structure (which will be discussed in more detail below) and is designed to absorb a significant amount of energy upon blade impingement during a Fan Blade Out (FBO) event. The fan impingement liner 36 incorporates a wear resistant layer 37. The front and rear acoustic liners 38, 39 are adhered to the fan containment case 32 adjacent the front and rear portions 34, 35, respectively. The fan containment case 32 serves as a rigid structural support for the fan impingement liner 36, wear layer 37, and acoustic liners 38 and 39.

The structure of the fan impingement liner 36 and the abradable layer 37 is shown in more detail in FIG. 3. The fan impingement liner 36 is composed of the following structural layers: an outer panel laminate 40; a low-density honeycomb structure 41 at an optimum angle; a first separator ply sub-laminate 42; braided reinforcing fiber sheet layer 43; a reinforcing fiber mat layer 44; a second separator layer sub-laminate 45; a high-density honeycomb structure 46; inner panel sub-laminate 47; and a wear-resistant layer 37 having a honeycomb structure.

The outer skin sub-laminate 40, the optimally angled low density honeycomb 41, the first membrane layer sub-laminate 42, the second membrane layer sub-laminate 45, the high density honeycomb 46, the inner skin sub-laminate 47 and the wear layer 37 are each formed from the same fibre reinforced polymer material, which in this example is a Carbon Fibre Reinforced Polymer (CFRP) material consisting of carbon fibres suspended in epoxy resin. However, the layers may also be formed of other suitable fibre-reinforced polymer materials in combination with reinforcing fibres, for example made of: aramid fibers (e.g. poly-p-phenylene terephthalamide)Or p-phenylene terephthalamide) Thermosetting liquid crystalline polyoxazoles (e.g. poly-p-phenylene-2, 6-benzobisoxazole (PBO or PBO)) Or ultra-high molecular weight polyethylene (UHMWPE), and polymeric matrix materials such as polyesters, vinyl esters, polyamides (e.g., nylon), polylactide, polycarbonate, or Acrylonitrile Butadiene Styrene (ABS).

Outer side panel sub-laminate 40, first membrane layer sub-laminate 42, second membrane layer sub-laminate 45, and inner side panel sub-laminate 47 are comprised of solid layers of CFRP material with reinforcing fibers aligned generally parallel to engine axis 9 or circumferentially around the fan track liner. The low density honeycomb 41, high density honeycomb 46, and abradable layer 37 at the optimum angles are composed of CFRP material arranged to form the cell walls of the honeycomb. The cells of the honeycomb are air-filled. The cell size of the low density honeycomb 41 at the optimum angle should be about 7 mm. The cell size of the high density honeycomb 46 should be about 3 mm. The cell size of the abrasion resistant layer 37 should be about 5 mm. The cell walls of the optimally angled low density honeycomb 41 are angled to align primarily with the predicted trajectory of the fan blade during an FBO event.

The outer side panel sub-laminate 40, the optimally angled low density honeycomb structure 41, the first membrane layer sub-laminate 42, the second membrane layer sub-laminate 45, the high density honeycomb structure 46, the inner side panel sub-laminate 47, and the wear layer 37 are integrally formed with each other such that the CFRP material extends continuously between all of the layers. Although the first and second membrane layer sub-laminates 42, 45 are shown in fig. 3 as being spaced apart from one another by the woven layers of reinforcing fiber sheets 43 and reinforcing fiber felt layers 44, these woven and felt layers do not extend along the entire axial length of the fan track liner 36 and are actually fully encapsulated at each axial end of the fan track liner 36 by the CFRP material extending between the first and second membrane layer sub-laminates 42, 45. In other examples, the woven and felt layers may include a plurality of discrete and angularly spaced layer elements to allow the CRFP material to extend between the first and second membrane layer sub-laminates 42, 45 at angular positions between the layer elements, and the respective woven and felt layers may extend the entire axial length of the fan track liner 36.

Woven reinforcing fiber sheet layer 43 and reinforcing fiber felt layer 44 together form ballistic barrier layer 48. In this embodiment, both the woven reinforcement fiber plies 43 and the reinforcement fiber mat 44 are made of poly (p-phenylene terephthalamide) (also known as) The reinforcing fibers of (2). However, both the braided sheet and the felt may be formed from reinforcing fibers of carbon, aramid, UHMWPE, PBO or other suitable high strength material. Woven fiber plies 43 may be any suitable fiber weave known in the art including plain weave, twill weave, segmented weave, basket weave, leno weave, or mock leno weave.

The fan track liner 36 is bonded to the inside surface of the fan containment case 32 by a layer of epoxy-based adhesive 49. The fan track liner 36 extends angularly completely around the engine in the area proximate the fan (i.e., completely around the inside circumference of the fan containment case 32).

The fan rail liner 36 is structured to absorb a significant amount of energy from the impinging fan blade during an FBO event. In particular, cellular structures are generally capable of absorbing impact energy through mechanical deformation through three conditions: an initial elastic deformation condition; a subsequent cell collapse condition in which the cell walls buckle and collapse due to plastic deformation; and finally a densified condition in which adjacent cell walls are compacted to one another and the relative density of the porous material is significantly increased. Thus, upon impact of a fan blade during an FBO event, the various layers of honeycomb material in the fan rail liner typically deform substantially, absorb energy, and decelerate the impacting blade.

In addition, ballistic barrier 48 further improves the impact resistance of fan track liner 36. The impact projectile reaching the ballistic barrier first comes into contact with the felt layer 43, which absorbs energy as the felt fibers are compressed and which itself molds around the projectile, thereby softening any sharp projectile edges. By slowing and covering the projectile, the felt layer reduces the likelihood that the projectile will be able to pierce woven sheet 42, thus providing increased strength to ballistic barrier layer 48. Together, the two layers of the ballistics barrier further reduce the likelihood of a ballistic projectile penetrating the fan containment case 32.

Because the fan track liner is made primarily of the same fiber reinforced polymer material, the coefficient of thermal expansion is effectively uniform in each of the layers 37, 40, 41, 42, 45 and 46. Accordingly, fan track liners typically expand or contract uniformly in response to changes in temperature. This reduces the likelihood of structural deformation such as warping or interface separation in response to temperature changes, particularly during manufacture of the fan rail liner or during bonding of the fan rail liner to the fan containment case, as described in more detail below.

Fan track liners are primarily manufactured using an additive manufacturing process known as Fused Deposition Modeling (FDM) or equivalent fuse fabrication (FFF). FDM involves the feeding of one or more input material filaments into a heated extruder head that melts some or all of the input material and deposits the molten material onto a substrate. A computer provided with a digital design model can be used to precisely control the deposition rate and the movement of the extruder head, allowing the layer-by-layer construction of complex three-dimensional structures.

Fiber reinforced polymer materials such as CFRP can now be deposited using FDM apparatus. In some cases, the fiber reinforced polymer material may be deposited by using composite fiber reinforced polymer material filaments as an input. In other cases, the fiber reinforced polymer material may be deposited by using separate polymer and reinforcing fiber filaments as inputs to a single extruder head. The continuous fiber reinforced polymer material and the discontinuous fiber reinforced polymer material may be deposited using FDM methods known in the art.

In fig. 4, a method for manufacturing a fan track liner is shown, wherein a fiber reinforced composite material is deposited on a cylindrical mandrel 50. The mandrel 50 is rotated about its longitudinal axis by rollers 51A and 51B. A movable FDM extruder head 52, which feeds the fiber reinforced polymer input material, is mounted on a frame 53 above the mandrel. The FDM extruder head may be controlled by a computer (not shown) to deposit fiber reinforced polymer material onto the rotating mandrel 50 to sequentially build up the plurality of different layers 37, 47, 46, 45, 42, 41 and 40 of the fan track liner around the circumference of the mandrel. Between the deposition of layers 45 and 42, the FDM deposition process may be paused, and may be performed by wrapping around the layers that have been deposited onto the mandrelFelt layer andthe sheets are woven to form the ballistic barrier layer. FDM deposition of the remaining layers 42, 41 and 40 may then proceed to encapsulate the felt and woven plies within the additively manufactured fan track liner structure.

The FDM process may use a thermoplastic polymer as an input material, in which case the process of manufacturing the fan track liner does not require a curing step, and the structure formed by the FDM process may be a complete fan track liner. However, the FDM device may have an input comprising a thermosetting polymer (such as epoxy). In this case, the structure formed by the FDM process may be a fan rail liner preform that must be cured to make the final fan rail liner. Curing the fan track liner preform typically involves heating the preform to the curing temperature of the matrix material and/or applying pressure to the preform. In particular, because most of the layers of the fan rail liner preform are printed using the same material, the distortion of the structure due to thermal expansion or contraction during curing is reduced, as compared to known fan rail liners that are typically manufactured by co-curing multiple layers of different materials that exhibit different thermal responses. Because fan track liners typically expand or contract relatively uniformly in response to changes in temperature, any remaining thermally induced structural deformations are also relatively simple to model and therefore are considered in manufacturing the overall fan containment arrangement.

The fan containment case 32 may also be formed around the same mandrel 50 used to form the fan track liner 36. The fan containment case may be manufactured using standard composite manufacturing techniques known in the art. For example, a fan containment case may be manufactured by first laying up a preform for a fan containment case around a fan track liner or fan track liner preform deposited on a mandrel, and then curing the fan containment case preform. Laying up the fan containment case preform may involve repeated application of layers, such as carbon fiber plies, to the mandrel. The carbon fibre plies may be applied in the form of carbon fibre tape, in particular pre-impregnated with an uncured matrix material such as uncured resin. Alternatively, the uncured matrix material may be injected into the fan containment case preform after the lay-up is complete. The fan case preform is then cured, typically by applying heat and/or pressure.

The fan track liner preform and the fan containment case preform may be co-cured, thereby reducing the number of curing steps required to form the fan containment arrangement. Alternatively, the fan casing preform may be first cured on a mandrel, and then the fan containment casing preform is then laid up around the cured fan casing and cured.

An alternative method for forming the fan track liner 36 is shown in FIG. 5, wherein the fiber-reinforced composite material is deposited directly inside the cured fan containment case 32. In this method, the fan containment case is rotated about its longitudinal axis by rollers 54A and 54B. A movable FDM extrusion head 55, which feeds the fiber reinforced polymer input material, is mounted on a movable arm 56, which is inserted into the hollow fan containment case. The movable arm and FDM extruder head are controlled by a computer (not shown) to deposit fiber reinforced polymer material onto the inside surface of the fan containment case 32 to sequentially build up a plurality of different layers 40, 41, 42, 45, 46, 47, and 37 of the fan track liner around the inside circumference of the fan containment case. Between the deposition of layers 42 and 45, the FDM deposition process may be paused, and may be performed by sputteringWoven sheet layer andthe felt layer is applied to the layer that has been deposited onto the interior of the fan containment case to form a ballistic resistant barrier layer. FDM deposition of the remaining layers 45, 46, 47 and 37 may then proceed to encapsulate the woven plies and felt layers within the additively manufactured fan track liner structure.

In the case where a thermoset polymer is used as the matrix material, the deposited fan track liner preform may be cured within the fan containment case by the application of heat and/or pressure. Because most of the layers of the fan rail liner preform are printed using the same material, structural distortion due to thermal expansion or contraction during curing is again reduced.

The skilled person will appreciate that the same FDM process may also be used to deposit fiber reinforced polymer material to form acoustic liners 38 and 39, either separate from the fan impingement liner 36 or in combination with the fan impingement liner 36.

Fig. 6 is a flow chart of a method of manufacturing a fan track liner, illustrating the steps described above with reference to fig. 4 and 5. At block 101, the FDM device has a digital model, for example in the form of an AMF or STL file, for a fan track liner. At block 102, a fiber reinforced polymer material is deposited onto a rotating mandrel or onto an inner surface of a fan containment case using an FDM apparatus to form a fan track liner according to a digital model.

FIG. 7 is a flow chart of an alternative method of manufacturing a fan track liner, illustrating the steps described above with reference to FIGS. 4 and 5. At block 103, the FDM device has a digital model, for example in the form of an AMF or STL file, for the fan rail liner preform. At block 104, a thermoset fiber reinforced polymer material is deposited onto the rotating mandrel, or onto the inner surface of the fan containment case, using an FDM device, forming a fan rail liner preform according to the digital model. At block 105, the fan rail liner preform is cured, such as by applying heat and/or pressure, to form a fan rail liner.

FIG. 8 is a flow chart of another alternative method of manufacturing a fan track liner, illustrating the steps described above with reference to FIGS. 4 and 5. At block 106, the FDM device has a digital model, for example in the form of an AMF or STL file, for the fan track liner. At block 107, a fiber reinforced polymer material is deposited onto the rotating mandrel, or onto an inner surface of the fan containment case, using the FDM device to form a first portion of the fan track liner according to the digital model. At block 108, a woven reinforcement fiber sheet layer and a reinforcement fiber mat layer are applied to a first portion of a fan track liner. The order of application of the braided reinforcing fiber sheet and the reinforcing fiber mat layer may vary depending on whether the fan track liner is deposited on the rotating mandrel or on the inner surface of the fan containment shell such that the reinforcing fiber mat layer is inside the braided reinforcing fiber sheet in the finished fan track liner. At block 109, a fiber reinforced polymer material is deposited using an FDM device onto a layer already formed on a rotating mandrel or fan containment shell to form a second portion of a fan track liner and to encapsulate a woven ply and felt layer between the first and second portions of the fan track liner.

FIG. 9 is a flow chart of another alternative method of manufacturing a fan track liner illustrating the steps described above with reference to FIGS. 4 and 5. At block 110, the FDM device has a digital model, for example in the form of an AMF or STL file, for the fan rail liner preform. At block 111, a thermoset fiber reinforced polymer material is deposited onto the rotating mandrel or onto the inner surface of the fan containment case using an FDM device to form a first portion of a fan track liner preform according to a digital model. At block 112, a layer of braided reinforcement fiber sheets and a layer of reinforcement fiber mat are applied to a first portion of the fan rail liner preform. The order of application of the braided reinforcing fiber sheet and the reinforcing fiber mat layer may vary depending on whether the fan track liner preform is deposited on the rotating mandrel or on the inner surface of the fan containment shell such that the reinforcing fiber mat layer is inside the braided reinforcing fiber sheet in the finished fan track liner. At block 113, a thermoset fiber reinforced polymer material is deposited using an FDM device onto a layer already formed on the rotating mandrel or fan containment shell to form a second portion of the fan track liner preform and to encapsulate the braid layer and the felt layer between the first portion and the second portion of the fan track liner preform. At block 114, the fan rail liner preform is cured, such as by applying heat and/or pressure, to form a fan rail liner.

It is to be understood that the present invention is not limited to the above-described embodiments, and various modifications and improvements may be made without departing from the concept described herein. Any feature may be used alone or in combination with any other feature or features unless mutually exclusive, and the disclosure extends to and includes all combinations and subcombinations of one or more features described herein.

For the avoidance of doubt, the invention extends to the subject matter set forth in the following numbered paragraphs:

1. a fan rail liner for a fan containment arrangement of a gas turbine engine, the fan rail liner comprising a porous impingement structure and a support sub-laminate integrally formed with one another from a fiber reinforced polymer material.

2. The fan track liner of paragraph 1, wherein the porous impingement structure is a honeycomb structure.

3. The fan track liner of paragraph 1 or paragraph 2, further comprising a ballistic barrier comprising a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt.

4. The fan rail liner of any preceding paragraph, wherein the porous impingement structure and the support sub-laminate are integrally formed with one another by additive manufacturing.

5. The fan track liner of any preceding paragraph, wherein the fiber reinforced polymer material comprises reinforcing fibers made from one or more of the following materials: carbon, aramid polymer, ultra-high molecular weight polyethylene, PBO.

6. The fan track liner of any preceding paragraph comprising two porous impingement structures separated from each other by a barrier layer formed from a support sub-laminate, and optionally wherein the two porous impingement structures have different cell densities.

7. A fan track liner according to any preceding paragraph, comprising two support panel sub-laminates, wherein one of the support panel sub-laminates forms an inner side of the fan track liner and the other of the support panel sub-laminates forms an outer side of the fan track liner, thereby forming a sandwich structure in which the porous impingement structure is located between the two support panel sub-laminates.

8. A fan containment arrangement for a gas turbine engine, the fan containment arrangement comprising a fan containment case and a fan track liner according to any preceding paragraph.

9. A method of manufacturing a fan rail liner or a fan rail liner preform for a fan containment arrangement of a gas turbine engine, the method comprising: depositing fiber reinforced polymer material by an additive manufacturing device to form a porous impingement structure and a support sub-laminate bonded to each other.

10. The method of paragraph 9, further comprising: providing or fabricating a digital model for the fan rail liner or the fan rail liner preform; and controlling the additive manufacturing apparatus using the digital model to deposit fiber reinforced polymer material to form the porous impingement structure and the support sub-laminate.

11. The method of paragraph 9 or paragraph 10, further comprising depositing the fiber reinforced polymer material onto a rotating mandrel.

12. The method of paragraph 11, further comprising: laying up a fan containment case preform around a fan track liner or fan track liner preform formed on a rotating mandrel; and curing the fan containment case preform and, optionally, if present, the fan track liner preform.

13. The method of paragraph 9 or 10, further comprising: depositing the fiber reinforced polymer material onto an inside surface of a fan containment case or fan containment case preform, such as an adhesive coated inside surface of a fan containment case or fan containment preform; and optionally, curing the fan rail liner preform and/or the fan containment case preform, if present.

14. A digital design model for a fan track liner according to any of paragraphs 1 to 7.

15. A computer program comprising instructions for causing an additive manufacturing apparatus to perform a method according to any of paragraphs 9 to 13 and/or make a fan track liner according to any of paragraphs 1 to 7.

16. A non-transitory computer readable medium storing the digital design model according to paragraph 14 and/or the computer program according to paragraph 15.

17. A data carrier signal carrying the digital design model according to paragraph 14 and/or the computer program according to paragraph 15.

18. A fan track liner for a fan containment arrangement of a gas turbine engine, the fan track liner comprising an embedded ballistic barrier comprising a woven layer of reinforcing fibers and a layer of reinforcing fiber felt, wherein optionally the woven layer of reinforcing fibers is disposed outside the layer of reinforcing fiber felt.

19. The fan track liner of paragraph 18, further comprising a porous impingement structure.

20. The fan track liner of paragraph 19 comprising two porous impingement structures separated from each other by a barrier layer comprising the ballistics barrier.

21. The fan track liner of any of paragraphs 18 to 20, wherein the woven reinforcement fiber sheet layer and the reinforcement fiber batt layer each comprise reinforcement fibers made of one or more of the following materials: carbon, aramid polymer, ultra-high molecular weight polyethylene, PBO.

22. A fan containment arrangement for a gas turbine engine, the fan containment arrangement comprising a fan containment case and a fan track liner according to any of paragraphs 18 to 21.

23. A method of manufacturing a fan track liner for a fan containment arrangement of a gas turbine engine, the method comprising: depositing a fibre reinforced polymer material, for example by an additive manufacturing device, to form a first portion of a fan rail liner or a fan rail liner preform; forming a ballistic resistant barrier layer on a first portion of the fan rail liner or the fan rail liner preform by applying a woven layer of reinforcing fiber sheets and a layer of reinforcing fiber felt; and depositing a fibre reinforced polymer material on and around the anti-ballistic barrier layer, for example by an additive manufacturing device, to form a second portion of the fan track liner or fan track liner preform, thereby encapsulating the anti-ballistic barrier layer between the first and second portions of the fan track liner or fan track liner preform; and, optionally, curing the fan track liner preform.

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